System and method for vaporizing space debris in space

Patent metadata

Field	Value
Publication number	US-11492150-B1
Application number	US-201916718938-A
Country	US
Kind code	B1
Filing date	Dec 18, 2019
Priority date	Sep 29, 2016
Publication date	Nov 8, 2022
Grant date	Nov 8, 2022

Abstract

A system and method for vaporizing space debris in space. The system includes a spacecraft body, a primary solar concentrator mounted to the spacecraft body that collects and focuses solar flux from the sun, and a secondary solar concentrator positioned at a focal point of the primary solar concentrator that refocuses the focused solar flux. A manipulator arm coupled to the spacecraft body grabs the space debris in space and positions it at a location where the refocused solar flux vaporizes the debris. The secondary solar concentrator can be a point-source concentrator, the primary solar concentrator can be a parabolic mirror, a Fresnel lens or a light focusing element or assembly, and the space debris can be a retired spacecraft or launch vehicle upper stage or component.

First claim

What is claimed is:

1. A system for vaporizing space debris in space,
said system comprising:
a spacecraft body;
a solar collection device mounted to the spacecraft body for collecting solar flux from the sun that is converted into heat; and
a manipulator device for grabbing the space debris and positioning it at a location in space where the heat from the solar flux vaporizes the space debris, wherein the solar collection device includes a first solar concentrator that is positioned to receive the solar flux and a second solar concentrator that is positioned at a focal point of the first solar concentrator, said second concentrator being operable to receive focused solar flux from the first solar concentrator and refocus the focused solar flux on the space debris.

2. The system according to claim 1 wherein the first solar concentrator is a parabolic mirror, a Fresnel lens or a light focusing element or assembly.

3. The system according to claim 1 wherein the second solar concentrator is a point-source concentrator.

4. The system according to claim 1 wherein the manipulator device is manipulator arm coupled to the spacecraft body.

5. The system according to claim 1 wherein the space debris is a retired spacecraft or launch vehicle upper stage or component.

6. A system for vaporizing space debris in space, said system comprising:
a spacecraft body;
a primary solar concentrator mounted to the spacecraft body and being configured to collect and focus solar flux from the sun;
a secondary solar concentrator positioned at a focal point of the primary solar concentrator and being configured to refocus the focused solar flux from the primary solar concentrator; and
a manipulator arm coupled to the spacecraft body for grabbing the space debris and being configured to position it at a location in space where the refocused solar flux vaporizes the space debris.

7. The system according to claim 6 wherein the secondary solar concentrator is a point-source concentrator.

8. The system according to claim 6 wherein the primary solar concentrator is selected from the group consisting of a parabolic mirror, a Fresnel lens and a light focusing element or assembly.

9. The system according to claim 6 wherein the space debris is a retired spacecraft or launch vehicle upper stage or component.

10. A method for vaporizing space debris in space, said method comprising:
providing a primary solar concentrator on a spacecraft body;
collecting and focusing solar flux from the sun by the primary solar collector;
providing a secondary solar concentrator at a focal point of the primary solar concentrator;
refocusing the focused solar flux by the secondary solar concentrator; and
positioning the space debris in space at a location where the refocused solar flux vaporizes the space debris.

11. The method according to claim 10 wherein the secondary solar concentrator is a point-source concentrator.

12. The method according to claim 10 wherein the primary solar concentrator is selected from the group consisting of a parabolic mirror, a Fresnel lens and a light focusing element or assembly.

13. The method according to claim 10 wherein the space debris is a retired spacecraft or launch vehicle upper stage or component.

Assignees

• Northrop Grumman Systems Corp

Inventors

• Eller Howard S

Classifications

• F27B14/10 Primary

  Crucibles · CPC title

• B22F12/44

  characterised by the configuration of the radiation means · CPC title

• B22F12/226

  for rotary motion · CPC title

• B64G4/00 Primary

  Tools specially adapted for use in space · CPC title

• B33Y30/00

  Apparatus for additive manufacturing; Details thereof or accessories therefor · CPC title